A method according to an aspect of the present invention includes determining if terrain presents a hazard to an aircraft based on the current position of the aircraft and the intended flight plan for the aircraft and providing an alert if it is determined that the terrain presents a hazard to the aircraft. The method may be employed in any situation to achieve any result, such as when the aircraft is in a low-RNP environment to prevent nuisance terrain alerts.
Legal claims defining the scope of protection, as filed with the USPTO.
1. A method comprising: determining, with a processor, if terrain presents a hazard to an aircraft based on a current position of the aircraft and an intended flight plan for the aircraft; and providing an alert if it is determined that the terrain presents a hazard to the aircraft; wherein determining if the terrain presents a hazard to the aircraft further includes at least one of: determining if the current position of the aircraft is within any of one or more boundaries, each boundary surrounding at least a portion of the intended flight plan; and determining if the terrain is within the one or more boundaries.
2. The method of claim 1 , wherein the one or more boundaries include an inner boundary and an outer boundary, and wherein the outer boundary at least partially surrounds the inner boundary.
3. The method of claim 2 , further comprising determining, with the processor, that the terrain presents a hazard to the aircraft when the terrain is located within the outer boundary and when an estimated trajectory for the aircraft conflicts with the terrain.
4. The method of claim 2 , further comprising determining, with the processor, that the terrain presents a hazard to the aircraft when the current position of the aircraft is located outside the inner boundary and when an estimated trajectory for the aircraft conflicts with the terrain.
5. The method of claim 2 , wherein one or more dimensions of at least one of the inner boundary and the outer boundary are selected based on at least one of: a normal flight technical error (FTE) for the aircraft; a navigation system error (NSE) for the aircraft; a required navigation performance (RNP) of a procedure performed by the aircraft; a required obstacle clearance (ROC) of a procedure performed by the aircraft; a total system error (TSE) for the aircraft; and a desired time period to respond to an alert.
6. The method of claim 2 , wherein one or more dimensions of at least one of the inner boundary and the outer boundary are selected based on one or more of: a bank angle for the aircraft; a rate of turn for the aircraft; a rate of acceleration for the aircraft; a status indicator of an autopilot aboard the aircraft; a vertical speed of the aircraft; a vertical velocity of the aircraft; a flight path angle of the aircraft; and a lateral navigation mode (LNAV) for the aircraft.
7. A medium storing instructions executable by a processor to perform a method, the medium being non-transitory and the method comprising: determining if terrain presents a hazard to an aircraft based on a current position of the aircraft and an intended flight plan for the aircraft; and providing an alert if it is determined that the terrain presents a hazard to the aircraft; wherein determining if the terrain presents a hazard to the aircraft further includes at least one of: determining if the current position of the aircraft is within one or more boundaries, each boundary surrounding at least a portion of the intended flight plan; and determining if the terrain is within the one or more boundaries.
8. The medium of claim 7 , wherein the one or more boundaries include an inner boundary and an outer boundary, and wherein the outer boundary at least partially surrounds the inner boundary.
9. The medium of claim 8 , wherein the method further comprises determining that the terrain presents a hazard to the aircraft when the terrain is located within the outer boundary and when an estimated trajectory for the aircraft conflicts with the terrain.
10. The medium of claim 8 , wherein the method further comprises determining that the terrain presents a hazard to the aircraft when the current position of the aircraft is located outside the inner boundary and when an estimated trajectory for the aircraft conflicts with the terrain.
11. A system comprising: a processor; a user interface; and a memory coupled to the processor and storing instructions that, when executed by the processor, cause the processor to: determine if the terrain presents a hazard to the aircraft based on a current position of the aircraft and an intended flight plan for the aircraft; and provide an alert to a user through the user interface if it is determined that the terrain presents a hazard to the aircraft; wherein determining if the terrain presents a hazard to the aircraft further includes at least one of: determining if the current position of the aircraft is within one or more boundaries, each boundary surrounding at least a portion of the intended flight plan; and determining if the terrain is within one or more of the boundaries.
12. The system of claim 11 , further comprising a flight management system in communication with the processor, the flight management system for providing the processor with information pertaining to the intended flight plan of the aircraft.
13. The system of claim 11 , wherein the one or more boundaries include an inner boundary and an outer boundary, and wherein the outer boundary at least partially surrounds the inner boundary.
14. The system of claim 13 , wherein the memory further stores instructions to cause the processor to determine that the terrain presents a hazard to the aircraft when the terrain is located within the outer boundary and when an estimated trajectory for the aircraft conflicts with the terrain.
15. The system of claim 13 , wherein the memory further stores instructions to cause the processor to determine that the terrain presents a hazard to the aircraft when the current position of the aircraft is located outside the inner boundary and when an estimated trajectory for the aircraft conflicts with the terrain.
16. The system of claim 13 , wherein one or more dimensions of at least one of the inner boundary and the outer boundary are selected based on at least one of: a normal flight technical error (FTE) for the aircraft; a navigation system error (NSE) for the aircraft; a required navigation performance (RNP) of a procedure performed by the aircraft; a required obstacle clearance (ROC) of a procedure performed by the aircraft; a total system error (TSE) for the aircraft; and a desired time period to respond to an alert.
17. The system of claim 13 , wherein one or more dimensions of at least one of the inner boundary and the outer boundary are selected based on one or more of: a bank angle for the aircraft; a rate of turn for the aircraft; a rate of acceleration for the aircraft; a status indicator of an autopilot aboard the aircraft; a vertical speed of the aircraft; a vertical velocity of the aircraft; a flight path angle of the aircraft; and a lateral navigation mode (LNAV) for the aircraft.
Cooperative Patent Classification codes for this invention. Click any code to explore related patents in that topic.
March 4, 2008
April 18, 2017
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